High data rate aircraft to ground communication antenna system

ABSTRACT

A method for ground to air communication includes receiving a first pilot signal on a first wide beam from a first ground base station by a first antenna element covering a first range of azimuth angles from an aircraft. Data is received on a directed data beam from the first ground base station by the first antenna element. A second pilot signal is received on a second wide beam from a second ground base station by a second antenna element covering a second range of azimuth angles different than the first range of azimuth angles. A signal strength of the second pilot signal is compared with a signal strength of the first pilot signal. Data reception is switched from the first antenna element to the second antenna element if the signal strength of the second pilot signal is greater than the signal strength of the first pilot signal.

CROSS-REFERENCE TO RELATED APPLICATION

The present Application for Patent is a divisional of U.S. patentapplication Ser. No. 13/168,538 filed Jun. 24, 2011, attorney docket111025U1, which claims the benefit of U.S. Provisional Application No.61/441,231 filed Feb. 9, 2011, in the names of M. Tassoudji et al.,attorney docket 111025P1, and assigned to the assignee hereof and herebyexpressly incorporated by reference herein in its entirety.

This application is related to commonly assigned U.S. patent applicationSer. No. 13/168,617 filed Jun. 24, 2011, entitled “REAL-TIME CALIBRATIONOF AN AIR TO GROUND COMMUNICATION SYSTEM,” in the names of A. JALALI etal. attorney docket 111025U2, and commonly assigned U.S. patentapplication Ser. No. 13/168,623 filed Jun. 24, 2011, entitled “GROUNDSTATION ANTENNA ARRAY FOR AIR TO GROUND COMMUNICATION SYSTEM” in thenames of A. JALALI et al., attorney docket 111025U3, the disclosures ofwhich are expressly incorporated by reference herein in theirentireties.

BACKGROUND

1. Field

Aspects of the present disclosure relate generally to wirelesscommunication systems, and more particularly for providing Internetservices to aircraft.

2. Background

Two main approaches provide Internet access to airplanes. In oneapproach, an Air to Ground (ATG) system uses terrestrial Ground BaseStations (GBS) using cellular communication techniques to provideInternet access to aircraft flying over land. A currently used ATGsystem operating over the continental United States uses only 3 MHz ofspectrum. Although, this system may become commercially viable, thelimited spectrum may be inadequate to accommodate increasing demand forInternet services, such as streaming of Internet content to aircraft. Inanother approach, satellite links provide Internet service to aircraft.The satellite based systems have more spectrum available but their costis excessive.

Because of the excessive cost of satellite links for aircraft Internetcommunication, it has been preferable to utilize the terrestrial basedATG systems. It would be desirable to increase available spectrum forATG and provide techniques that would allow such systems to accommodatethe increasing demands for aircraft Internet service withoutsubstantially increasing cost.

SUMMARY

According to one aspect of the present disclosure, a method for groundto air communication with an aircraft equipped with a multi-beamaircraft array antenna is described. The method includes receiving afirst pilot signal on a first wide beam from a first ground base stationof a network by a first antenna element of the aircraft antenna array.In one aspect, the first antenna element covers a first range of azimuthangles from the aircraft. Data may be received data on a directed databeam from the first ground base station by the first antenna element.The method includes receiving a second pilot signal on a second widebeam from at least one second ground base station of the network by asecond antenna element of the aircraft antenna array. In one aspect, thesecond antenna element covers a second range of azimuth angles from theaircraft different than the first range of azimuth angles. A signalstrength of the second pilot signal may be compared with a signalstrength of the first pilot signal. In one aspect, the method includesswitching reception of the data from the first antenna element to thesecond antenna element in response to determining that signal strengthof the second pilot signal received by the second antenna element isgreater than the signal strength of the first pilot signal received onthe first antenna element.

In another aspect, an apparatus for ground to air communication in awireless network in which an aircraft is equipped with a multi-beamaircraft array antenna is described. The apparatus includes means forreceiving a first pilot signal on a first wide beam from a first groundbase station by a first antenna element covering a first range ofazimuth angles from an aircraft. The apparatus also includes means forreceiving data on a directed data beam from the first ground basestation by the first antenna element. The apparatus also includes meansfor receiving a second pilot signal on a second wide beam from a secondground base station by a second antenna element covering a second rangeof azimuth angles different than the first range of azimuth angles. Theapparatus also includes means for comparing a signal strength of thesecond pilot signal with a signal strength of the first pilot signal. Inone aspect, the apparatus includes means for switching data receptionfrom the first antenna element to the second antenna element if thesignal strength of the second pilot signal is greater than the signalstrength of the first pilot signal.

In another aspect, a computer program product for ground to aircommunication in a wireless network in which an aircraft is equippedwith a multi-beam aircraft array antenna is described. The computerprogram product includes a computer-readable medium having program coderecorded thereon. The computer program product has program code toreceive a first pilot signal on a first wide beam from a first groundbase station by a first antenna element covering a first range ofazimuth angles from an aircraft. The computer program produce alsoincludes program code to receive data on a directed data beam from thefirst ground base station by the first antenna element. The computerprogram product also includes program code to receive a second pilotsignal on a second wide beam from a second ground base station by asecond antenna element covering a second range of azimuth anglesdifferent than the first range of azimuth angles. The computer programproduct also includes program code to compare a signal strength of thesecond pilot signal with a signal strength of the first pilot signal. Inone aspect, the computer program product also includes program code toswitch data reception from the first antenna element to the secondantenna element if the signal strength of the second pilot signal isgreater than the signal strength of the first pilot signal.

In yet another aspect, an apparatus for ground to air communication in awireless network in which an aircraft is equipped with a multi-beamaircraft array antenna is described. The apparatus includes at least oneprocessor; and a memory coupled to the at least one processor. Theprocessor(s) is configured to receive a first pilot signal on a firstwide beam from a first ground base station by a first antenna elementcovering a first range of azimuth angles from an aircraft. Theprocessor(s) is further configured to receive data on a directed databeam from the first ground base station by the first antenna element.The processor(s) is further configured to receive a second pilot signalon a second wide beam from a second ground base station by a secondantenna element covering a second range of azimuth angles different thanthe first range of azimuth angles. The processor(s) is furtherconfigured to compare a signal strength of the second pilot signal witha signal strength of the first pilot signal. In one aspect, theprocessor(s) is further configured to switch data reception from thefirst antenna element to the second antenna element if the signalstrength of the second pilot signal is greater than the signal strengthof the first pilot signal.

This has outlined, rather broadly, the features and technical advantagesof the present disclosure in order that the detailed description thatfollows may be better understood. Additional features and advantages ofthe disclosure will be described below. It should be appreciated bythose skilled in the art that this disclosure may be readily utilized asa basis for modifying or designing other structures for carrying out thesame purposes of the present disclosure. It should also be realized bythose skilled in the art that such equivalent constructions do notdepart from the teachings of the disclosure as set forth in the appendedclaims. The novel features, which are believed to be characteristic ofthe disclosure, both as to its organization and method of operation,together with further objects and advantages, will be better understoodfrom the following description when considered in connection with theaccompanying figures. It is to be expressly understood, however, thateach of the figures is provided for the purpose of illustration anddescription only and is not intended as a definition of the limits ofthe present disclosure.

BRIEF DESCRIPTION OF THE DRAWINGS

The features, nature, and advantages of the present disclosure willbecome more apparent from the detailed description set forth below whentaken in conjunction with the drawings in which like referencecharacters identify correspondingly throughout.

FIG. 1 is a block diagram conceptually illustrating an example of an airto ground communication system according to an aspect of the presentdisclosure.

FIG. 2 is a diagram conceptually illustrating an example of an aircraftantenna system according to an aspect of the present disclosure.

FIG. 3A is a diagram conceptually illustrating an example of a simulatedgain pattern vs. an elevation angle of each antenna element of FIG. 1over an infinite ground plane according to an aspect of the presentdisclosure.

FIG. 3B is a diagram conceptually illustrating an example of a simulatedgain pattern vs. an azimuth angle of adjacent antenna elements of FIG. 1and a combined beam according to an aspect of the present disclosure

FIG. 5 is a block diagram conceptually illustrating a ground stationantenna array system according to one aspect of the present disclosure.

FIG. 6 is a block diagram conceptually illustrating a ground stationantenna array system according to a further aspect of the presentdisclosure.

FIG. 7 is a flow diagram showing a process for real-time calibration ofan air to ground two-way communication system including a ground stationantenna array system according to an aspect of the present disclosure.

FIG. 8 is a flow diagram showing a process for air to groundcommunication by an aircraft equipped with a multi-beam switchable arrayantenna according to an aspect of the present disclosure.

FIG. 9 is a flow chart illustrating a process for increasing atransmission power on a forward link from a serving ground base stationto mitigate aircraft interference according to one aspect of the presentdisclosure.

DETAILED DESCRIPTION

The detailed description set forth below, in connection with theappended drawings, is intended as a description of variousconfigurations and is not intended to represent the only configurationsin which the concepts described herein may be practiced. The detaileddescription includes specific details for the purpose of providing athorough understanding of the various concepts. However, it will beapparent to those skilled in the art that these concepts may bepracticed without these specific details. In some instances, well-knownstructures and components are shown in block diagram form in order toavoid obscuring such concepts.

The spectrum available for Internet communication to aircraft byterrestrial Air to Ground (ATG) systems has been limited for practicaland economic reasons. Providing seamless communication with aircraftflying at high altitudes over a large area (such as the continentalU.S.) involves spectrum that is available over the large area. That is,the spectrum assigned to the ATG system should be available nationwide.It has been problematic, however, to identify a portion of spectrum thatis available nationwide, much less arranging to free up such a portionof spectrum that has been allocated for other uses.

A large amount of spectrum has been assigned to geostationary satellitesfor use in broadcast TV and two way FSS (Fixed Satellite Service).Aspects of the present disclosure provide a high data rate aircraft toground communication antenna system for sharing portions of the spectrumbetween ATG applications and geostationary satellite communicationsystems. Frequency bands such as C band (4 GHz downlink, 6 GHz uplink),Ku band (12 GHz downlink, 14 GHz uplink) and Ka band (20 GHz downlink,30 GHz uplink) are currently used by geostationary satellite systems. Inone aspect, a high data rate aircraft to ground communications antennasystem may share the Ku uplink band to provide an aircraft with Internetservice.

Aspects of the present disclosure provide methods and apparatus for anATG system in which Ground Base Stations (GBSs) in communication withaircraft transceivers (ATs) in airplanes can use an uplink portion ofspectrum assigned for satellite systems without intolerable interferencewith communications on the satellite systems. The systems and techniquesdescribed in the present disclosure may allow coexistence of theincumbent satellite system and the new ATG system on the same spectrumwith negligible cross interference between the two systems.

A system 100 for wireless communication according to an illustrativeaspect of the present disclosure is described in FIG. 1. In one aspect,the system 100 includes a ground base station 102 that transmits andreceives signals on a satellite uplink band using a forward link (FL)108 and a reverse link (RL) 106. An aircraft transceiver (AT) 120 incommunication with the ground base station 102 may also transmit andreceive signals on the satellite uplink band using the forward link 108and reverse link 106. In one aspect, the aircraft transceiver 120 mayinclude a multi-beam switchable array antenna. Another ground basestation 110 is also shown.

In one aspect, the aircraft transceiver 120 may include an aircraftantenna that is comprised of a multi-beam switchable array that is ableto communicate with the ground base station 102 at any azimuth angle.The aircraft antenna may be mounted below the fuselage with a smallprotrusion and aerodynamic profile to reduce or minimize wind drag. Inone aspect, the antenna elevation coverage is from approximately 3° to10° below horizon. The antenna array may include N elements positionedsuch that each element directs a separate beam at different azimuthangles, each covering 360/N degrees, for example, as shown in FIG. 2.

FIG. 2 shows one example of an aircraft antenna array system 200 havingmultiple twelve-beam arrays 202 (202-1, . . . , 202-N) operating at, forexample, 14 gigahertz (GHz). Representatively, the aircraft antennaarray 202-1 has twelve horn antennas 210 (210-1, . . . , 210-12) eachcovering 30° sectors in azimuth with an aperture size of approximately2.0 inches'0.45 inches, and having a gain of >10 dBi (dB isotropic). Inone aspect, an overall diameter of the antenna array is roughly 8inches.

Although FIG. 2 illustrates the aircraft antenna arrays 202 in atwelve-beam array configuration, it should be recognized that otherconfigurations are possible while remaining within the scope of thepresent disclosure and appended claims. In particular, one exampleconfiguration includes four-antenna arrays 202 in a four-beam arrayconfiguration. In one aspect, the multiple aircraft antenna arrays 202enable ground base station search at different elevations. In oneaspect, the multiple antenna arrays 202 enable sectorization of theground base station antenna search in elevation. In this aspect, eachelement is coupled to its own transceiver. As described in furtherdetail below, the ground base station search enables a handoff betweenthe aircraft transceiver 120 and a next ground base station, such as aground base station 110, as shown in FIG. 1.

In one aspect, the aircraft antenna array system 200 is mounted belowthe fuselage and an auxiliary antenna is mounted onto a separate portionof the aircraft to improve aircraft Internet service. In particular,banking or rolling of the aircraft during flight may interruptcommunication between the aircraft antenna array system 200 mountedbelow the fuselage and the ground base station 102. In one aspect, theauxiliary antenna reduces disruption of the communication between theaircraft transceiver 120 and the ground base station 102 when theaircraft banks or rolls by handling the communications with the groundbase station during these times. Characteristics of the aircraft antenna200 are further illustrated in FIGS. 3A and 3B.

FIG. 3A illustrates a diagram 300 of a simulated elevation gain patternof a single antenna element 210 at azimuth angles of 0, 5, 10, 15 and 20degrees, according to one aspect of the present disclosure.Representatively, the x-axis in FIG. 3A represents the theta angle inspherical coordinates where the horizon is at 90°. Because thesimulation is performed over an infinite ground plane, the gain patternabove horizon (between −90 and 90) is duplicated due to image theory andshould be ignored. FIG. 3B shows a diagram 350 of the simulated azimuthgain pattern 352 and 354 of two adjacent elements and a digitallycombined beam 360 according to one aspect of the present disclosure.

Operation of the aircraft antenna 200 for providing aircraft Internetservice involves detection and aircraft modem handoff between a currentground base station 102 and a next ground base station 110, as shown inFIG. 1. Various schemes of communication and searching can be employedby the antenna system. In one aspect, a single receive chain is used forcommunication, with searching being performed in a sequential, timedivision manner. In another aspect, two receive chains may be used, withone chain for ground station communication and the other chain forground base station search. In the two receive chain configuration, thesearching chain can also be used for diversity combining to increase thegain and throughput while not searching. Ground base station search maybe performed as follows.

In one aspect, ground base station search may include a search of allpilot signals received from ground base stations on a given aircraftantenna element. The received pilot signals are ranked to determinewhether or not the aircraft modem should handoff to another ground basestation from which it is receiving a stronger pilot signal. Once thesearch on one antenna element is complete, the search may switch toanother element and repeat the pilot search on that element. In oneaspect, each of antenna elements 210-2 to 210-12 may continually searchfor ground stations while data is received by antenna element 210-1, asshown in FIG. 2.

In the configurations described above, a switched antenna schemeinvolves a transceiver that switches between different antenna elementsto achieve high gain while maintaining low complexity. Alternatively,the directional beams may be formed by combining multiple antennaelements using phased array techniques. In one aspect, the switchedantenna scheme described above may combine two adjacent beams 352 and354 to form combined beam 360 for further increasing the antenna gainwhile only slightly increasing the hardware complexity to providediversity. In one aspect, the switched antenna scheme may use a partialphased array beam combining of adjacent antenna elements. For example,adjacent beams may be combined to improve system performance when acommunicating ground base station is at or near a boundary of theadjacent beams.

FIG. 4 shows a block diagram of a design of a ground base station 102and an aircraft transceiver 120. The ground base station 102 may beequipped with antennas 434 a through 434 t, and the aircraft transceiver120 may be equipped with antennas 452 a through 452 r.

At the ground base station 102, a transmit processor 420 may receivedata from a data source 412 and control information from acontroller/processor 440. The processor 420 may process (e.g., encodeand symbol map) the data and control information to obtain data symbolsand control symbols, respectively. The processor 420 may also generatereference symbols. A transmit (TX) multiple-input multiple-output (MIMO)processor 430 may perform spatial processing (e.g., precoding) on thedata symbols, the control symbols, and/or the reference symbols, ifapplicable, and may provide output symbol streams to the modulators(MODs) 432 a through 432 t. Each modulator 432 may process a respectiveoutput symbol stream (e.g., for OFDM, etc.) to obtain an output samplestream. Each modulator 432 may further process (e.g., convert to analog,amplify, filter, and upconvert) the output sample stream to obtain adownlink/forward link signal. Downlink signals from modulators 432 athrough 432 t may be transmitted via the antennas 434 a through 434 t,respectively.

At the aircraft transceiver 120, the antennas 452 a through 452 r mayreceive the downlink/forward link signals from the ground base station102 and may provide received signals to the demodulators (DEMODs) 454 athrough 454 r, respectively. Each demodulator 454 may condition (e.g.,filter, amplify, downconvert, and digitize) a respective received signalto obtain input samples. Each demodulator 454 may further process theinput samples (e.g., for OFDM, etc.) to obtain received symbols. A MIMOdetector 456 may obtain received symbols from all the demodulators 454 athrough 454 r, perform MIMO detection on the received symbols ifapplicable, and provide detected symbols. A receive processor 458 mayprocess (e.g., demodulate, deinterleave, and decode) the detectedsymbols, provide decoded data for the aircraft transceiver 120 to a datasink 460, and provide decoded control information to acontroller/processor 480.

On the reverse link/uplink, at the aircraft transceiver 120, a transmitprocessor 464 may receive and process data from a data source 462 andcontrol information from the controller/processor 480. The processor 464may also generate reference symbols for a reference signal. The symbolsfrom the transmit processor 464 may be precoded by a TX MIMO processor466 if applicable, further processed by the modulators 454 a through 454r, and transmitted to the ground base station 102. At the ground basestation 102, the uplink/reverse link signals from the aircrafttransceiver 120 may be received by the antennas 434, processed by thedemodulators 432, detected by a MIMO detector 436 if applicable, andfurther processed by a receive processor 438 to obtain decoded data andcontrol information sent by the aircraft transceiver 120. The processor438 may provide the decoded data to a data sink 439 and the decodedcontrol information to the controller/processor 440.

The controllers/processors 440 and 480 may direct the operation at theground base station 102 and the aircraft transceiver 120, respectively.The processor 440 and/or other processors and modules at the ground basestation 102 may perform or direct the execution of various processes forthe techniques described herein. The processor 480 and/or otherprocessors and modules at the aircraft transceiver 120 may also performor direct the execution of the functional blocks illustrated in usemethod flow chart of FIG. 8, and/or other processes for the techniquesdescribed herein. The memories 442 and 482 may store data and programcodes for the ground base station 102 and the aircraft transceiver 120,respectively.

Ground station antenna array systems including antenna arrays forcommunicating with aircraft antenna 200 are shown in FIGS. 5 and 6according to aspects of the present disclosure. In one aspect, a groundstation antenna array system may include high gain multi-beam antennaarrays capable of communicating with multiple aircrafts simultaneously,for example, as shown in FIGS. 5 and 6. FIGS. 5 and 6 show two examplesof the sectorization and antenna array configurations according toaspects of the present disclosure.

In one aspect, sectorization may include splitting sectors in elevationto increase system throughput, for example, as shown in FIGS. 5 and 6.Representatively, the coverage region in azimuth and elevation may bedivided into narrow regions where the antenna array can maintain itsgain requirement over all angles in the coverage area. In oneconfiguration, the antennas may be operated in the 14 GHz range with acoverage region of 120° in azimuth and 0.5° to 10° in elevation. Theground base station antenna gain may be 40 dBi at 0.5° elevation and isreduced to 25.5 dBi at 10° elevation due to lower path loss to theaircraft.

Referring again to FIG. 5, FIG. 5 depicts a configuration of a groundbase station antenna array system 500 with two antenna panels 510 and530 each covering 60° in azimuth. In one aspect, each antenna panel510/530 may consist of an N×M array 520/540 of antenna elements 522(522-1, . . . , 522-N), 524 (524-1, . . . , 524-N), 542 (542-1, . . . ,542-N), and 544 (544-1, . . . , 544-N), respectively, which may bereferred to herein as ground station antenna arrays. In one aspect, eachantenna element includes a transmit/receive (T/R) module.Representatively, ground station antenna arrays 520 and 540 include 50×6antenna elements; however, other configurations are possible whileremaining within the scope of the described aspects and appended claims.In one aspect, digital beam forming may be employed to combine thesignal and achieve the overall gain desired. The digital beam formingmay be computed over the antenna elements in different columns and rowsof each panel.

FIG. 6 depicts a configuration of a ground station antenna array system600 in which number of antenna panels 610, 620, 630, and 640/650, 660,670, and 680 covering the elevation is increased to four and the numberof panels 602 and 604 covering the azimuth is maintained at two. In oneaspect, the aperture size for the panels (610/650) covering higherelevations is smaller than the aperture size for the panels (640/680)covering low elevations due to lower gain required at higher elevations.Each antenna array 612 (612-1, . . . , 612-N)/650 (650-1, . . . , 650-N)may include 50×1 elements where digital beam forming is applied. In oneaspect, generation of the digital beam is switched, for example, betweenadjacent panels 610/650 to next adjacent panels 620/660 depending on anelevation of the aircraft.

Other configurations that utilize a smaller number of elements fordigital beam forming can be achieved by further reducing the coverageregion of each panel in azimuth and increasing the antenna aperture ofthe elements while maintaining the array size. This can lead to a largeroverall ground station antenna array size but less complicated digitalsignal processing. In one aspect, a single element can be used for eachsector without any digital beam forming, which corresponds to 100×4antennas in the above example.

In one aspect, digital beam forming may be used in each array to providemultiple steerable pencil-beams. The signal for each element of thearray may pass through a T/R (transmit/receive) module and is convertedinto baseband. In one aspect, the phase shifts for a directional beamare calculated by a beam steering computer and applied to each signal.Similar phase factors may be applied to the transmit signal and passedthrough the transmit/receive module into the antenna element. In oneaspect, a calibration procedure equalizes the amplitude and phase ofeach element and accounts for the time variation of the circuitry.

As mentioned above, calibration compensates for the differentphase/amplitude responses of the antenna and transmit/receive units. Onetype of calibration may be performed in the factory using built incircuitry. This calibration may use any well known technique. The builtin calibration scheme may also be used for periodic calibration in thefield to track changes due to temperature and aging. Another approachfor calibration may be built into the air interface to provide real-timecalibration while performing two-way communication between a ground basestation and an aircraft modem. In one aspect, calibration isperiodically performed using the communication signaling of an airinterface. In particular, an over the air (OTA) real-time calibrationmay be performed while an air to ground two-way communication systemoperates.

In one aspect, the Forward Link (FL) on the Ground Base Station (GBS)unit periodically transmits a pilot signal on a wide beam that coversthe whole sector. As described herein, the periodically transmittedpilot signal on the forward link of the ground base station may bereferred to as a Sector Wide Pilot (SWP). In one aspect, the sector widepilot may allow an aircraft to detect new ground base stations, tosynchronize to the ground base stations, and to receive systemparameters, such as information on a periodic calibration proceduredescribed below. For example, as shown in FIG. 1, the ground basestation 102 may transmit a sector wide pilot over forward link 108.

In one aspect, the wide beam used to transmit the sector wide pilot maybe formed by transmitting on any of the individual ground stationantenna array elements (522, 524, 542, 544, 612, or 650), for example,as shown in FIGS. 5 and 6. The aircraft modem may detect this sectorwide pilot as part of its search procedure. One possible real timeprocedure to calibrate the transmit elements of the ground stationantenna array elements is performed as follows.

In one aspect, the ground base station periodically enters a calibrationmode. The time of the calibration mode may be sent on the forward linkon the same wide beam that carries the sector wide pilot. Calibratingthe transmit side of the ground station antenna array may be initiallyperformed. In particular, the ground base station transmitter maysequentially send the sector wide pilot on all ground station antennaarray elements during a time period assigned to calibration. Followingdemodulation, the signal received at the aircraft from the k-th groundstation antenna array element is given by:

(α_(K)e^(−jθ) ^(k) )(β_(k)e^(−jφ) ^(k) )(δ_(K)e^(−jν) ^(k))(σ_(k)e^(−j∂) ^(k) )   (1)

In equation (1), the first term may correspond to gain (α_(k)) and delay(θ_(k)) in the RF chain. The second term may correspond to the amplitude(β_(k)) and phase (φ_(k)) of coupling between antenna elements. Thethird term may correspond to amplitude (δ_(k)) the phase (ν_(k)) fromantenna array spacing. The last term may correspond to multipath fadingamplitude (σ_(k)) and phase ({circumflex over (ν)}_(k)). Also, j inequation (1) represents the imaginary part of a complex number.]

In one aspect, the first three terms are due to the hardware and can beestimated by averaging out the last term by making a number of temporalmeasurements. For instance, given the high speed at which the aircrafttravels, channel changes occur very rapidly (e.g., on the order ofmilliseconds). In on aspect, a number of measurements of equation (1)may be made over two millisecond intervals. These separate measurementsmay then be filtered to average out the last term in equation (1), whichis due to multi-path. In equation (1), the last term may assume thateither the channel is frequency non-selective or that the measurementsare made over a narrow bandwidth such as on individual tones of an OFDM(orthogonal frequency division multiplexing) physical layer.

In one aspect for a wide bandwidth system, the signals may be sent on asufficient number of tones to ensure calibration of the hardware overall frequencies. The aircraft modem may compute the calibrationcoefficients as described above and transmits the coefficients to theground base station so the ground base station may use thesecoefficients for forward link beam forming toward the aircraft, forexample, as shown in FIG. 1.

A process for real-time calibration of an air to ground two-waycommunication system may be performed as follows. FIG. 7 is a flow chartillustrating a method 700 for real-time calibration of an air to groundtwo-way communication system including a ground station antenna arraysystem according to one aspect of the present disclosure. At processblock 702, the air to ground two-way communication system operates toprovide Internet service for an aircraft, for example, as shown inFIG. 1. At process block 704 it is determined whether a calibrationperiod is detected during operation of the air to ground two-waycommunication system. Until a calibration period is detected, operationof the air to ground two-way communication system continues. Once acalibration period is detected, calibration of a base station antennasystem may be performed as follows.

At process block 706, a sector wide pilot signal is sequentiallytransmitted on a wide beam by each antenna element of a base stationantenna array. In one aspect, the antenna 500 (FIG. 5) may transmit aSector Wide Pilot (SWP) on each element of the ground station antennaarrays 520 and 540. In the configuration illustrated in FIG. 6, theground station antenna system 600 may transmit the sector wide pilot onone of the adjacent antenna panels 610 and 650, 620 and 660, 630 and670, or 640 and 680 depending on an elevation of the aircraft.

Referring again to FIG. 7, at process block 708 forward link calibrationcoefficients of the antenna array may be received from an aircraft inresponse to the sector wide pilot signals during the calibrationperiods. In one aspect, the calibration coefficients characterize thesector wide pilot signals received by the aircraft. At process block710, real-time calibration of an antenna array of the ground stationantenna array system is performed according to the received calibrationcoefficients using, for example, equation (1) in accordance with oneaspect of the present disclosure.

In one aspect, the receive side calibration may be performed in a mannersimilar to the above scheme but by having the aircraft modem transmit apilot sequence on the Reverse Link (RL) 106, as shown in FIG. 1. Thepilot signal may be sent with a sufficient amount of energy and with asufficient amount of time duration to enable detection at each of theantenna elements at the ground base station. Similar to the schemedescribed above for calibrating the transmit chain, in one aspect thereceive chain's phase and amplitude may be estimated by averaging overany variations due to multipath fading.

Once the ground base station and aircraft antennas are calibrated, beamforming may be performed in any number of ways. In one aspect, theaircraft sends its position to the ground base station based on acurrent position location, which may be determined with, for example, aposition location system such as a global positioning system (GPS). Theground base station may use this information to form a beam in thedirection of the aircraft and also on the receive side at the groundbase station. In a calibrated antenna system, knowledge of the positionof the aircraft and the ground base station can be used to calculate thephased array antenna coefficients to point the bore sight of the beamtoward the location of the aircraft. During the flight, the beam may beadjusted using the position of the aircraft that is periodicallyreported to the ground base station, according to one aspect of thepresent disclosure.

In one aspect, the aircraft and the ground base station may adjust theirbeams to increase or maximize Signal to Noise Plus Interference (SINR)received at the aircraft and at the ground base station. For instance,the ground base station may slightly move its transmit beam. Theaircraft will report SINR measurements received at the aircraft to theground base station. In one aspect, the ground base station may find theimproved or optimal transmit beam by adjusting its beam based on theSINR feedback received from the aircraft. In one aspect, the ground basestation may send one or more adjacent beams to determine whether one ofthe adjacent beams provides improved performance based on, for example,measured signal energy. In one aspect, detection of an improved oroptimal beam may be used on the reverse link from the aircraft to theground base station.

In TDD (Time Division Duplex) channels where the forward link andreverse link are reciprocal, except for the hardware phase and delayswhich are calibrated, the ground base station may determine the desiredor best received beam by comparing SINRs received on adjacent beams.Then, the ground base station may form a beam toward the aircraft basedon the desired or optimal beam on its receive side. In one aspect, theground base station repeatedly determines the desired or optimal receivebeam and adjusts the transmit beam accordingly. A process for air toground communication by an aircraft equipped with a multi-beamswitchable array antenna may be performed as follows.

FIG. 8 is a flow chart illustrating a method 800 for air to groundcommunication by an aircraft equipped with multiple antenna arrays of amulti-beam switchable antenna elements according to one aspect of thepresent disclosure. At process block 802, a first pilot signal isreceived on a wide beam from a first ground station of a network by afirst antenna element of an antenna. In one aspect, the antenna 200(FIG. 2) may receive a Sector Wide Pilot (SWP) on a first antennaelement 210 (210-1, . . . , 210-12) covering a first range of azimuthangles from the aircraft. In the configuration illustrated in FIG. 2,the aircraft antenna 200 has twelve horn antennas 210 (210-1, . . . ,210-12) each covering 30° sectors in azimuth.

Referring again to FIG. 8, at process block 804 data is received on adirected beam from the first ground station by the first antenna element(e.g. 210-1). At process block 806, at least one second pilot signal isreceived on a wide beam from at least one second ground station of thenetwork by a second antenna element of the antenna covering a secondrange of azimuth angles from the aircraft different than the first rangeof azimuth angles. For example, a sector wide pilot may be received fromthe second ground station 110 while data is being received from thefirst ground base station 102, as shown in FIG. 1.

As shown in FIG. 2, data may be received by the first antenna element210-1 while a sector wide pilot is received by the second antennaelement 210-2. In one configuration, each of the antenna elements 210-2to 210-12 may continually search for ground stations while data isreceived by the antenna element 210-1. In an alternative aspect, a timedivision mode operates by using a single antenna element for receivingdata, and when data is not being received, the remaining antennaelements may search for ground stations to determine whether to performan aircraft modem handoff.

Referring again to FIG. 8, at process block 808 a signal strength of thesecond pilot signal(s) is compared with a signal strength of the firstpilot signal. At process block 810, reception of the data may beswitched from the first antenna element to the second antenna element inresponse to determining that the second pilot signal strength receivedby the second antenna is greater than the first pilot signal strengthreceived on the first antenna element. In one aspect, the method 800, asshown in FIG. 8, is repeated for each aircraft antenna array 202 (FIG.2) for configurations having multiple aircraft antenna arrays. In analternative aspect, the method 800 is performed for a selected aircraftantenna array (e.g. 202-1).

Transmissions from non-geostationary satellite terminals may interferewith communications from a ground base station to an aircrafttransceiver on a served aircraft. Also, other aircraft may interferewith communications from a ground base station to an aircrafttransceiver on the served aircraft. In addition, signal degradation maybe caused by rain when either the Ka band or the Ku band is used by anair to ground communication system. Aspects of the present disclosuremay mitigate this type of interference and signal degradation to theaircraft terminal

As shown in FIG. 1, the transmission power on the forward link 108 ofground base station 102 may be increased to overcome interference, withan equal decrease in the forward link transmission power of the groundbase station 110. In one aspect, a ground base stationcontroller/processor 440 (FIG. 4) is responsible for adjusting thetransmission power among the various base stations so that the sum ofthe overall transmission power over the various ground base stationsremains constant.

In particular, the aircraft receiver may measure the Signal toInterference plus Noise Ratio (SINR) and send an index of the measuredSINR to the ground base station. In one aspect, the ground base stationadjusts the transmit power on the forward link beam to maintain the SINRreceived at the aircraft above a target value. In case of rain, thesignal becomes attenuated, resulting in a reduction in the received SINRat the aircraft. Each beam may be allowed a maximum transmit power. Thebase station controller will impose a limit on the overall transmitpower from all ground base stations. In case of interference from othersystems into the aircraft receiver, the interference term of SINR willincrease, reducing the SINR received by the aircraft. In one aspect, theground base station controller may increase the forward link power inresponse to the SINR feedback from the aircraft modem.

FIG. 9 is a flow chart illustrating a method 900 for increasing atransmission power on the forward link from a serving ground basestation to mitigate aircraft interference according to one aspect of thepresent disclosure. At process block 902, interference is detectedduring transmission of data on a forward link of a ground base stationantenna array from the serving ground base station to the aircraft. Atprocess block 904, the serving ground base station may increase atransmission power on the forward link to mitigate aircraftinterference. In one aspect, increasing the transmission power for theserving ground base station involves an equal decrease in transmissionpower of one or more other ground base stations. Accordingly, at processblock 906, a decrease in transmission power of one or more other groundbase stations is performed. In one aspect, the decrease in transmissionpower is performed so that the sum of the overall transmission powerover the various ground base stations remains constant.

In one configuration, an aircraft is configured for wirelesscommunication including means for receiving a first pilot signal on afirst wide beam from a first ground base station of a network. In oneaspect, the first pilot receiving means may be a first antenna element210-1 of the aircraft antenna array 200, as shown FIG. 2 and/or theantenna 452 a-r, demodulator 454 a-r, receive processor 458,controller/processor 480, and/or memory 482 of FIG. 4. The aircraft isalso configured to include a means for receiving data on a directed databeam from the first ground base station. In one aspect, the datareceiving means may be the first antenna element 210-1 of the aircraftantenna array 200, as shown FIG. 2 and/or the antenna 452 a-r,demodulator 454 a-r, receive processor 458, controller/processor 480,and/or memory 482 of FIG. 4. The aircraft is also configured to includea means for receiving a second pilot signal on a first wide beam fromthe first ground base station. In one aspect, the second pilot receivingmeans may be a second antenna element 210-2 of the aircraft antennaarray 200, as shown FIG. 2 and/or the antenna 452 a-r, demodulator 454a-r, receive processor 458, controller/processor 480, and/or memory 482of FIG. 4.

The aircraft is also configured to include a means for comparing asignal strength of the second pilot signal with a signal strength of thefirst pilot signal. In one aspect, the comparing means may be anaircraft transceiver 120 of the aircraft antenna array 200, as shownFIGS. 1, 2, and 4, the controller/processor 480, and/or memory 482 ofFIG. 4. The aircraft is also configured to include a means for switchingreception of the data from the first antenna element to the secondantenna element. In one aspect, the switching means may also be theaircraft transceiver 120 of the aircraft antenna array 200, as shownFIGS. 1 and 2, the controller/processor 480, and/or memory 482 of FIG.4. In another aspect, the aforementioned means may be a module or anyapparatus configured to perform the functions recited by theaforementioned means.

In one configuration, a ground base station is configured for wirelesscommunication including means for detecting interference during datatransmission on the forward link from the serving ground base station toan aircraft. In one aspect, the detecting means may be the demodulators432 a-t, receive processor 438, antenna 434 a-t, controller/processor440, and/or memory 442 of FIG. 4. The ground base station is alsoconfigured to include a means for increasing a transmission power on theforward link from the ground base station to mitigate aircraftinterference according to one aspect of the present disclosure. In oneaspect, the increasing means may the controller/processor 440, memory442, transmit processor 420, modulators 432 a-t, and/or antenna 434 a-tof FIG. 4. The ground base station is also configured to include a meansfor decreasing the transmission power of one or more other ground basestations. In one aspect, the decreasing means may also be thecontroller/processor 440, and/or memory 442 of FIG. 4. In anotheraspect, the aforementioned means may be a module or any apparatusconfigured to perform the functions recited by the aforementioned means.

Those of skill would further appreciate that the various illustrativelogical blocks, modules, circuits, and algorithm steps described inconnection with the disclosure herein may be implemented as electronichardware, computer software, or combinations of both. To clearlyillustrate this interchangeability of hardware and software, variousillustrative components, blocks, modules, circuits, and steps have beendescribed above generally in terms of their functionality. Whether suchfunctionality is implemented as hardware or software depends upon theparticular application and design constraints imposed on the overallsystem. Skilled artisans may implement the described functionality invarying ways for each particular application, but such implementationdecisions should not be interpreted as causing a departure from thescope of the present disclosure.

The various illustrative logical blocks, modules, and circuits describedin connection with the disclosure herein may be implemented or performedwith a general-purpose processor, a digital signal processor (DSP), anapplication specific integrated circuit (ASIC), a field programmablegate array (FPGA) or other programmable logic device, discrete gate ortransistor logic, discrete hardware components, or any combinationthereof designed to perform the functions described herein. Ageneral-purpose processor may be a microprocessor, but in thealternative, the processor may be any conventional processor,controller, microcontroller, or state machine. A processor may also beimplemented as a combination of computing devices, e.g., a combinationof a DSP and a microprocessor, a plurality of microprocessors, one ormore microprocessors in conjunction with a DSP core, or any other suchconfiguration.

The steps of a method or algorithm described in connection with thedisclosure herein may be embodied directly in hardware, in a softwaremodule executed by a processor, or in a combination of the two. Asoftware module may reside in RAM memory, flash memory, ROM memory,EPROM memory, EEPROM memory, registers, hard disk, a removable disk, aCD-ROM, or any other form of storage medium known in the art. Anexemplary storage medium is coupled to the processor such that theprocessor can read information from, and write information to, thestorage medium. In the alternative, the storage medium may be integralto the processor. The processor and the storage medium may reside in anASIC. The ASIC may reside in a user terminal In the alternative, theprocessor and the storage medium may reside as discrete components in auser terminal.

In one or more exemplary designs, the functions described may beimplemented in hardware, software, firmware, or any combination thereofIf implemented in software, the functions may be stored on ortransmitted over as one or more instructions or code on acomputer-readable medium. Computer-readable media includes both computerstorage media and communication media including any medium thatfacilitates transfer of a computer program from one place to another. Astorage media may be any available media that can be accessed by ageneral purpose or special purpose computer. By way of example, and notlimitation, such computer-readable media can comprise RAM, ROM, EEPROM,CD-ROM or other optical disk storage, magnetic disk storage or othermagnetic storage devices, or any other medium that can be used to carryor store desired program code means in the form of instructions or datastructures and that can be accessed by a general-purpose orspecial-purpose computer, or a general-purpose or special-purposeprocessor. Also, any connection is properly termed a computer-readablemedium. For example, if the software is transmitted from a website,server, or other remote source using a coaxial cable, fiber optic cable,twisted pair, digital subscriber line (DSL), or wireless technologiessuch as infrared, radio, and microwave, then the coaxial cable, fiberoptic cable, twisted pair, DSL, or wireless technologies such asinfrared, radio, and microwave are included in the definition of medium.Disk and disc, as used herein, includes compact disc (CD), laser disc,optical disc, digital versatile disc (DVD), floppy disk and blu-ray discwhere disks usually reproduce data magnetically, while discs reproducedata optically with lasers. Combinations of the above should also beincluded within the scope of computer-readable media.

The previous description of the disclosure is provided to enable anyperson skilled in the art to make or use the disclosure. Variousmodifications to the disclosure will be readily apparent to thoseskilled in the art, and the generic principles defined herein may beapplied to other variations without departing from the spirit or scopeof the disclosure. Thus, the disclosure is not intended to be limited tothe examples and designs described herein but is to be accorded thewidest scope consistent with the principles and novel features disclosedherein.

What is claimed is:
 1. A method for ground to air communication with anaircraft equipped with a multi-beam aircraft array antenna, comprising:detecting interference during transmission of data on a forward link ofa ground base station antenna array from a ground base station to theaircraft; increasing a transmission power on the forward link of theground base station antenna array; and decreasing a transmission poweron a forward link of at least one other ground base station to maintaina constant total transmission power over all ground base stations of anair to ground two-way communication system.
 2. The method of claim 1, inwhich detecting interference comprises: receiving a Signal toInterference plus Noise Ratio (SINR) value from the aircraft; anddetecting interference when the received SINR value is below apredetermined target value.
 3. The method of claim 1, in whichincreasing the transmission power further comprises: adjusting thetransmission power on the forward link of the ground base stationantenna array to maintain a measured Signal to Interference plus NoiseRatio (SINR) value at the aircraft above a target value.
 4. An apparatusfor wireless communication, comprising: means for detecting interferenceduring transmission of data on a forward link of a ground base stationantenna array from a ground base station to an aircraft; means forincreasing a transmission power on the forward link of the ground basestation antenna array; and means for decreasing a transmission power ona forward link of at least one other ground base station to maintain aconstant total transmission power over all ground base stations of anair to ground two-way communication system.
 5. The apparatus of claim 4,in which the detecting means further comprises: means for receiving aSignal to Interference plus Noise Ratio (SINR) value from the aircraft;and means for detecting interference if the received SINR value is belowa predetermined target value
 6. The apparatus of claim 4, in which theincreasing means further comprises: means for adjusting the transmissionpower on the forward link of the ground base station antenna array tomaintain a measured Signal to Interference plus Noise Ratio (SINR) valueat the aircraft above a target value.
 7. A computer program product forwireless communication in a wireless network, comprising: anon-transitory computer-readable medium having non-transitory programcode recorded thereon, the program code comprising: program code todetect interference during transmission of data on a forward link of aground base station antenna array from a ground base station to anaircraft; program code to increase a transmission power on the forwardlink of the ground base station antenna array; and program code todecrease a transmission power on a forward link of at least one otherground base station to maintain a constant total transmission power overall ground base stations of an air to ground two-way communicationsystem.
 8. An apparatus for wireless communication, comprising: amemory; and at least one processor coupled to the memory, the at leastone processor being configured: to detect interference duringtransmission of data on a forward link of a ground base station antennaarray from a ground base station to an aircraft; to increase atransmission power on the forward link of the ground base stationantenna array; and to decrease a transmission power on a forward link ofat least one other ground base station to maintain a constant totaltransmission power over all ground base stations of an air to groundtwo-way communication system.
 9. The apparatus of claim 8, in which theat least one processor is further configured to detect by: receiving aSignal to Interference plus Noise Ratio (SINR) value from the aircraft;and detecting interference if the received SINR value is below apredetermined target value
 10. The apparatus of claim 8, in which the atleast one processor is further configured to increase transmission powerby adjusting the transmission power on the forward link of the groundbase station antenna array to maintain a measured Signal to Interferenceplus Noise Ratio (SINR) value at the aircraft above a target value.